[Federal Register Volume 81, Number 133 (Tuesday, July 12, 2016)]
[Proposed Rules]
[Pages 45075-45079]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-16322]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7426; Directorate Identifier 2015-NM-199-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 737-100, -200, and -200C series 
airplanes. This proposed AD is intended to complete certain mandated 
programs intended to support the airplane reaching its limit of 
validity (LOV) of the engineering data that support the established 
structural maintenance program. This proposed AD would require 
repetitive detailed, high frequency eddy current (HFEC), and ultrasonic 
inspections of the center section rear spar upper clevis lugs and 
horizontal stabilizer rear spar upper lugs, as applicable, for any 
cracking, and related investigative and corrective actions if 
necessary. For certain airplanes, this proposed AD would require 
replacement of the center section rear spar upper chord with a new part 
and a serviceable center section assembly. This proposed AD would also 
require repetitive HFEC and fluorescent dye penetrant inspections of 
the center section for cracking of the front and rear spar upper clevis 
lugs or horizontal stabilizer front and rear spar upper lugs, and 
related investigative and corrective actions if necessary. We are 
proposing this AD to detect and correct cracking in the rear spar upper 
clevis lugs of the center section, and in the rear spar upper lugs of 
the horizontal stabilizer which could result in the loss of structural 
integrity and controllability of the airplane.

DATES: We must receive comments on this proposed AD by August 26, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P. O. Box 
3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-5000, 
extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7426.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for

[[Page 45076]]

and locating Docket No. FAA-2016-7426; or in person at the Docket 
Management Facility between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this proposed AD, the 
regulatory evaluation, any comments received, and other information. 
The street address for the Docket Office (phone: 800-647-5527) is in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Payman Soltani, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5313; fax: 562-627-5210; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2016-7426; 
Directorate Identifier 2015-NM-199-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs 
have been developed to support initiatives that will ensure the 
continued airworthiness of aging airplane structure. The last element 
of those initiatives is the requirement to establish a LOV of the 
engineering data that support the structural maintenance program under 
14 CFR 26.21. This proposed AD is the result of an assessment of the 
previously established programs by the DAH during the process of 
establishing the LOV for the affected airplanes. The actions specified 
in this proposed AD are necessary to complete certain programs to 
ensure the continued airworthiness of aging airplane structure and to 
support an airplane reaching its LOV.
    This proposed AD is intended to complete certain mandated programs 
intended to support the airplane reaching its LOV of the engineering 
data that support the established structural maintenance program. An 
operator detected a cracked center section at the rear spar upper chord 
clevis lug. This condition, if not corrected, could result in cracking 
in the rear spar clevis lugs of the horizontal stabilizer center 
section, which could result in loss of structural integrity and 
controllability of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-55A1033, Revision 2, 
dated August 7, 2015. The service information describes procedures for 
repetitive detailed, HFEC, and ultrasonic inspections of the center 
section rear spar upper clevis lugs and rear spar upper lugs of the 
horizontal stabilizer; HFEC and fluorescent dye penetrant inspections 
for cracking in the front and rear spar upper clevis lugs of the center 
section and the front and rear spar upper lugs of the horizontal 
stabilizer. For certain airplanes, the service information describes 
procedures for replacement of the center section rear spar upper chord 
with a new part and replacing the center section with a serviceable 
center section assembly, or installing bushings and sleeves as 
applicable. This service information is reasonably available because 
the interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between This Proposed AD and the Service 
Information.'' For information on the procedures and compliance times, 
see this service information at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-7426.
    The phrase ``related investigative actions'' is used in this NPRM. 
Related investigative actions are follow-on actions that (1) are 
related to the primary action, and (2) further investigate the nature 
of any condition found. Related investigative actions in an AD could 
include, for example, inspections.
    The phrase ``corrective actions'' is also used in this NPRM. 
Corrective actions are actions that correct or address any condition 
found. Corrective actions in an AD could include, for example, repairs.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 
7, 2015, specifies to contact the manufacturer for certain 
instructions, but this proposed AD would require accomplishment of 
repair methods, modification deviations, and alteration deviations in 
one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.
    Where Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated 
August 7, 2015, specifies a compliance time or repeat interval as 
``Horizontal Stabilizer Center Section flight cycles'' or ``Horizontal 
Stabilizer flight cycles,'' this AD requires compliance for the 
corresponding time or repeat interval in airplane flight cycles.

Costs of Compliance

    We estimate that this proposed AD affects 84 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                             Parts                              Cost on U.S.
              Action                      Labor cost          cost      Cost per product          operators
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Repetitive detailed, HFEC, and      9 work-hours x $85            $0  $765 per inspection   $64,260 per
 ultrasonic inspections.             per hour = $765 per               cycle.                inspection cycle.
                                     inspection cycle.

[[Page 45077]]

 
Repetitive HFEC and fluorescent     118 work-hours x $85           0  $10,030 per           $842,520 per
 dye penetrant inspections.          per hour = $10,030                inspection cycle.     inspection cycle.
                                     per inspection cycle.
Replacement.......................  Up to 252                 25,000  Up to $46,420 per     Up to $3,899,280 per
                                     work[dash]hours x                 inspection cycle.     inspection cycle.
                                     $85 per hour =
                                     $21,420 per
                                     inspection cycle.
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    We estimate the following costs to do any necessary inspections, 
repairs, and replacements that would be required based on the results 
of the proposed inspection. We have no way of determining the number of 
aircraft that might need these inspections, repairs, and replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                      Labor cost        Parts cost              Cost per product
----------------------------------------------------------------------------------------------------------------
Bolt and Bushing Removal/            101 work-hours x $85            $0  $8,585.
 Inspection, Fabrication, and         per hour = $8,585.
 Installation.
Repair and replacement.............  Up to 252                   25,000  Up to $46,420 per inspection cycle.
                                      work[dash]hours x
                                      $85 per hour =
                                      $21,420 per
                                      inspection cycle.
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Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2016-7426; Directorate Identifier 
2015-NM-199-AD.

(a) Comments Due Date

    We must receive comments by August 26, 2016.

(b) Affected ADs

    This AD affects AD 84-23-05, Amendment 39-4949 (49 FR 45744, 
November 20, 1984); and AD 86-12-05, Amendment 39-5321 (51 FR 18771, 
May 22, 1986).

(c) Applicability

    This AD applies to The Boeing Company Model 737-100, -200, and -
200C series airplanes, certificated in any category, as identified 
in Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated 
August 7, 2015.

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This proposed AD is intended to complete certain mandated 
programs intended to support the airplane reaching its limit of 
validity (LOV) of the engineering data that support the established 
structural maintenance program. We are issuing this AD to detect and 
correct cracking in the rear spar upper clevis lugs of the center 
section, and in the rear spar upper lugs of the horizontal 
stabilizer which could result in the loss of structural integrity 
and controllability of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspections, Related Investigative and Corrective Actions (Service 
Information Tables 1 and 3)

    At the applicable time specified in table 1 or table 3 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-55A1033, Revision 2, dated August 7, 2015, except as specified 
in paragraph (o) of this AD: Do detailed, high frequency eddy 
current (HFEC), and ultrasonic inspections of the center section 
rear spar upper clevis lugs for any cracking, and do all applicable 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
55A1033, Revision 2, dated August 7, 2015; except as specified in 
paragraph (p) of this AD. Do all related investigative and 
corrective actions before further flight. Repeat the inspections 
thereafter at the applicable times specified in table 1 or table 3 
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-55A1033, Revision 2, dated August 7, 2015.

(h) Replacement (Service Information Table 1)

    For airplanes identified as Group 1, Configuration 1, in Boeing 
Alert Service

[[Page 45078]]

Bulletin 737-55A1033, Revision 2, dated August 7, 2015: At the 
applicable time specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, 
Revision 2, dated August 7, 2015, except as specified in paragraph 
(o) of this AD, replace the center section rear upper chord with a 
new part or replace the center section with a serviceable center 
section assembly, in accordance with the Accomplishment Instructions 
of Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated 
August 7, 2015.

(i) Repetitive Post-Replacement Inspections, Related Investigative and 
Corrective Actions (Service Information Table 2)

    For airplanes identified as Group 1, Configuration 1, in Boeing 
Alert Service Bulletin 737-55A1033, Revision 2, dated August 7, 
2015, with a new or serviceable 0.932-inch-thick center section rear 
spar upper chord: At the applicable time specified in table 2 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-55A1033, Revision 2, dated August 7, 2015, except as specified 
in paragraph (o) of this AD, do detailed, HFEC, and ultrasonic 
inspections of the center section rear spar upper chord clevis lugs 
for any cracking, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-55A1033, Revision 
2, dated August 7, 2015; except as specified in paragraph (p) of 
this AD. Do all related investigative and corrective actions before 
further flight. Repeat the inspections thereafter at the applicable 
times specified in table 2 of paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 
7, 2015.

(j) Post-Replacement Inspections, Related Investigative and Corrective 
Actions (Service Information Table 4)

    For airplanes on which the center section rear spar upper chord 
was last replaced with a new part or serviceable part: Within the 
applicable times specified in table 4 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, 
Revision 2, dated August 7, 2015, except as specified in paragraph 
(o) of this AD, do detailed, HFEC, and ultrasonic inspections of the 
center section rear spar upper chord clevis lugs for any cracking, 
and do all applicable related investigative and corrective actions, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015; 
except as specified in paragraph (p) of this AD. Do all related 
investigative and corrective actions before further flight. Repeat 
the inspections thereafter at the applicable times specified in 
table 4 of 1.E., ``Compliance'' of Boeing Alert Service Bulletin 
737-55A1033, Revision 2, dated August 7, 2015.

(k) Repetitive Inspections, Related Investigative and Corrective 
Actions of the Horizontal Stabilizer (Service Information Table 5)

    Within the applicable time specified in table 5 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, 
Revision 2, dated August 7, 2015, except as specified in paragraph 
(o) of this AD, do detailed, HFEC, and ultrasonic inspections of the 
rear spar upper lugs of the horizontal stabilizer for any cracking, 
and do all applicable related investigative and corrective actions, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015; 
except as specified in paragraph (p) of this AD. Do all related 
investigative and corrective actions before further flight. Repeat 
the inspections thereafter at the applicable times specified in 
table 5 of 1.E., ``Compliance'' of Boeing Alert Service Bulletin 
737-55A1033, Revision 2, dated August 7, 2015.

(l) Post Replacement Inspections, Related Investigative and Corrective 
Actions (Service Information Table 6)

    For airplanes with a replaced horizontal stabilizer with a new 
or serviceable part, within the applicable times specified in table 
6 of 1.E., ``Compliance'' of Boeing Alert Service Bulletin 737-
55A1033, Revision 2, dated August 7, 2015, except as specified in 
paragraph (o) of this AD: Do a detailed, HFEC, and ultrasonic 
inspection of the rear spar upper lugs of the horizontal stabilizer 
for any cracking, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-55A1033, Revision 
2, dated August 7, 2015; except as specified in paragraph (p) of 
this AD. Do all related investigative and corrective actions before 
further flight. Repeat the inspections thereafter at the applicable 
times specified in table 6 of 1.E., ``Compliance'' of Boeing Alert 
Service Bulletin 737-55A1033, Revision 2, dated August 7, 2015.

(m) Scheduled Inspections, Related Investigative and Corrective Actions 
(Service Information Table 7)

    Within the applicable times specified in table 7 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, 
Revision 2, dated August 7, 2015, except as specified in paragraph 
(o) of this AD: Do HFEC and fluorescent dye penetrant inspections 
for cracking in the front and rear spar upper clevis lugs of the 
center section and front and rear spar upper lugs of the horizontal 
stabilizer, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-55A1033, Revision 
2, dated August 7, 2015; except as specified in paragraph (p) of 
this AD. Do all related investigative and corrective actions before 
further flight. Repeat the inspections thereafter at the applicable 
times specified in table 7 of paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 737-55A1033, Revision 2, dated August 
7, 2015.

(n) Post Scheduled Inspections, Related Investigative and Corrective 
Actions (Service Information Table 8)

    For airplanes on which the center section rear spar upper chord 
or horizontal stabilizer rear spar upper chord has been replaced: 
Within the applicable time specified in table 8 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, 
Revision 2, dated August 7, 2015, except as specified in paragraph 
(o) of this AD: Do HFEC and fluorescent dye penetrant inspections 
for cracking in the front and rear spar upper clevis lugs of the 
center section or front and rear spar upper lugs of the horizontal 
stabilizer, as applicable, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
55A1033, Revision 2, dated August 7, 2015; except as specified in 
paragraph (p) of this AD. Do all related investigative and 
corrective actions before further flight. Repeat the inspections 
thereafter at the applicable times specified in table 8 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1033, 
Revision 2, dated August 7, 2015.

(o) Exceptions to the Service Information: Compliance Times

    (1) Where Boeing Alert Service Bulletin 737-55A1033, Revision 2, 
dated August 7, 2015, specifies a compliance time ``after the 
Revision 2 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Where Boeing Alert Service Bulletin 737-55A1033, Revision 2, 
dated August 7, 2015, specifies a compliance time or repeat interval 
as ``Horizontal Stabilizer Center Section flight cycles'' or 
``Horizontal Stabilizer flight cycles,'' this AD requires compliance 
for the corresponding time or repeat interval in airplane flight 
cycles.

(p) Exception to the Service Information: Repair Compliance Method

    If any cracking of the lug is found during any inspection 
required by this AD, and Boeing Alert Service Bulletin 737-55A1033, 
Revision 2, dated August 7, 2015, specifies to contact Boeing for 
appropriate action: Before further flight, repair the lug using a 
method approved in accordance with the procedures specified in 
paragraph (r) of this AD.

(q) Terminating Actions

    (1) For Model 737-100, -200, and -200C series airplanes: 
Accomplishment of the inspections specified in paragraph (g) of this 
AD terminates the requirements of paragraph A. of AD 84-23-05, 
Amendment 39-4949 (49 FR 45744, November 20, 1984).
    (2) For Model 737-200 and -200C series airplanes: Accomplishment 
of the inspections specified in paragraph (m) and (n) of this AD 
terminates the requirements of paragraphs A. and B. of AD 86-12-05, 
Amendment 39-5321 (51 FR 18771, May 22, 1986).

(r) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the

[[Page 45079]]

attention of the person identified in paragraph (s)(1) of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Los Angeles ACO, to make those findings. To be approved, 
the repair method, modification deviation, or alteration deviation 
must meet the certification basis of the airplane and the approval 
must specifically refer to this AD.

(s) Related Information

    (1) For more information about this AD, contact Payman Soltani, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5313; fax: 562-627-5210; email: [email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-
5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on June 28, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2016-16322 Filed 7-11-16; 8:45 am]
 BILLING CODE 4910-13-P